Aerospace technic and technology最新文献

{"title":"Використання систем автоматизованого проектування для підвищення точності механічної обробки","authors":"Maryna Filippova, M. Demchenko, Denis Smolnikov, Natalia Bezuglaya, Halina Bohdan","doi":"10.32620/aktt.2023.2.03","DOIUrl":"https://doi.org/10.32620/aktt.2023.2.03","url":null,"abstract":"The subject of the study is methods and means of determining the influence of the trajectory of the tool on the foreground of the volume of complex parts. The aim is to improve the quality and accuracy of the production of composite profile parts after machining at CNC machining centers, by using the optimal machining strategy. Task: to analyze existing methods of processing complex profile parts at CNC processing centers and justify the choice of the optimal strategy for the side of the surface of the part. The methods used are: methods of controlling the accuracy of processing complex surfaces, graphical methods of forming the trajectory of the tool, and mechanical methods of measuring geometric dimensions. The results obtained are as follows. To achieve this goal, an analysis of existing methods and strategies for processing surfaces of a complex profile was carried out and the existing experience in the development of control programs was adapted using automated methods with the application of CAD/CAM systems. As a result, SolidWorks was chosen as the primary modeling tool for creating a part with a complex profile. The tool path is created using the SolidCAM CAM system, which supports various strategies for processing such elements. Using the developed control programs based on the methods of linear trajectory, bitmap trajectory, spiral trajectory, and waterline trajectory, experimental analysis of the influence of the tool trajectory on the accuracy of processing surfaces located at different angles to the processing axis was carried out. Deviations of geometrical dimensions of parts obtained in re-treatment by programs formed using different methods from the real values of model characteristics are evaluated. Conclusions. Based on the analysis of the strategies for processing parts of a complex profile, the optimal trajectories of the tool are determined for parts with surfaces such as at a low angle, at a high angle, radius surface, and joints between surfaces. The results of experimental studies in further shaping of folding parts when they are prepared on CNC machine with the choice of the optimal trajectory of the movement of the tool. The choice of the optimal trajectory of the processing of parts allows to increase the accuracy of the processing in finishing operations.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127911878","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Шляхи адаптації та модернізації випробувального обладнання для відтворення ударних навантажень виходячи з вимог стандарту MIL-STD-810","authors":"Oleh Zlatkin, Oleksii Chumachenko, Inna Kryzhyvets, Oleksii A. Petrov, Yurii Torba","doi":"10.32620/aktt.2023.1.08","DOIUrl":"https://doi.org/10.32620/aktt.2023.1.08","url":null,"abstract":"The subject matter of the article is the process of testing the objects of general use, aviation and space industry, railway transport, electric power industry, and nuclear industry on the impact of shock loads. The goal is to implement modern international standards, in particular MIL-STD-810, in the practice of testing laboratories. The tasks to be solved are: to study the possibility of using vibration stands in impact testing and to modernize the existing test equipment by developing a new software for control systems based on existing and proven algorithms. To achieve this goal, the analysis of current regulatory documents was carried out and the existing experience in the conformity assessment was adapted. The following results were obtained: a research test stand was created using the technical capabilities of the Test & Certification Center of RPI “HARTRON-ARKOS” LTD. The software was developed using standard library elements from the SCADA system. The capacity of using a vibrating stand during impact testing was taken into account, and an iterative impact control mode was implemented. The operability of the modernized test equipment was confirmed by full-scale verification of all parameters with a positive result, and approbation was passed during real tests in various modes for complex test objects. This paper formulates proposals for expanding the capabilities of the existing laboratory and testing base when implementing MIL-STD-810. The proposed approach to software development allows the replication of the code in any other software environment. A comparative assessment of financial and time costs for the purchase of new and modernization of existing equipment confirms the economic feasibility of the described approach. The perceptiveness of the adoption of the MIL-STD-810 standard as a state standard of Ukraine was defined. It is proposed to use this standard in the practice of testing laboratories to conform the requirements of developers and manufacturers in various industries, as well as a basis for industry standards, which ensures the replacement of outdated and canceled standards.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127490635","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Методологія формування предметної області модифікаційних змін у важкому транспортному літаку","authors":"Oleksandr Dveirin, Viktor Riabkov, Liudmyla V. Kapitanova, Danylo Kirnoson","doi":"10.32620/aktt.2023.1.01","DOIUrl":"https://doi.org/10.32620/aktt.2023.1.01","url":null,"abstract":"The subject of study is the process of forming the parameters of modification changes in a heavy transport aircraft. The goal is to develop the subject area of modification changes with the help of design models. The task is  to develop models for determining the parameters of modification changes of the base aircraft based on the subject area of the modification project, namely: a model of the decomposition of modification changes of the base aircraft with the selection of parameter levels, which made it possible to apply more reliable assessment methods for different groups of parameters; a model of displaying the structure of the base aircraft in the subject area of the modification project, which uses the concepts of similarity and equivalence, it allows to highlight the necessary modification changes of the base aircraft; a temporal model of tracking efficiency changes, taking into account the time interval of creating modifications; a model for assessing the feasibility of modification changes in lower-level parameters, taking into account additional labor costs for their implementation. All this makes it possible to increase the reliability of the technical and economic justification of the modification. The methods used are following: an analytical method of defining the subject area using a system of new criteria that allow evaluating the integral characteristics of the aircraft modification for the benefit of different participants at different stages of the creation of the modification: for project developers, specific cost criteria are adopted as the ratio of all types of costs to all useful work, performed by the modification at the stage of its operation; for the stage of flight tests and production development in modifications –  the criterion for the expediency of modification changes, taking into account the labor costs for their implementation; for operating airlines – the technology of formation of flight parameters, which provide a \"niche\" of competitiveness of modifications and temporary tariffs for the benefit of the consumer. The obtained scientific results: allow to form subject areas of promising modifications of heavy transport aircraft, which can reasonably compete in the world markets of aircraft and air transportation. Conclusion. The scientific novelty of the obtained results is as follows: the proposed model for determining the subject area of modification changes of the base aircraft. This makes it possible to set the parameters of modification changes in the aircraft at the stage of aircraft design, and thereby ensure its competitiveness in the aircraft and air transportation markets.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126927883","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Методика проведення чисельного дослідження камери імпульсного детонаційного двигуна","authors":"O.S. Aksonov","doi":"10.32620/aktt.2023.1.05","DOIUrl":"https://doi.org/10.32620/aktt.2023.1.05","url":null,"abstract":"The subject of research in this article is the process of detonation propagation in the chamber of a pulse detonation engine. Experimental research on detonation engines is a complex and expensive process that requires high-speed, high-precision equipment to obtain high-quality reliable results. Therefore, to conduct preliminary research, numerical experiment methods using mathematical simulation tools should be used. This work analyzes the possibility of applying known calculation models to study the detonation propagation process in the chamber of a pulse detonation engine. The task: to study the influence of the application of existing calculation models on the accuracy of numerical simulation of the detonation process; analyze the use of existing calculation models for the study of the detonation propagation process. The main method used in this work is the method of mathematical simulation using CFD technologies. The following results were obtained. The work considered the application of various turbulence models, chemical transition models, solvers and mesh sizes in modeling processes in the chamber of a pulse detonation engine. The application k-ε and k-ω turbulence models and their modifications are considered. The closest to the real result is obtained when applying k-ω model turbulence with SST modification. Generalized modification of this model averages the parameters on the front of the detonation wave, which leads to the destruction of the structure of the front. Taking into account the peculiarities of the processes occurring at the front of the detonation wave, the eddy-dissipation concept method will be better for modeling chemical transition, compared to the finite-rate method. Using the finite-rate method shows instantaneous combustion at the front of the detonation wave. This leads to a sharp increase in the parameters at the detonation front with its further separation from the main flow. To obtain a qualitatively reliable result of the parameters at the front of the detonation wave, cell dimensions of no more than 1/16 mm should be used. The application of the eddy-dissipation concept method with k-ω SST turbulence model allows obtaining the closest results to the experimental data. The deviation of pressure and velocity values obtained during modeling does not exceed 5% from their actual values. The temperature deviation does not exceed 10%. This is determined by the selected kinetic scheme of chemical transitions. All considered models and methods affect only the structure and development of the detonation wave front. There are no significant differences in the values of the parameters along the front (in the Taylor zone). Conclusion. The obtained results are of practical importance for the design and research of detonation engines. The use of the proposed calculation models will allow conducting numerical experiments for the pulse detonation engine chamber with sufficient accuracy, in comparison with experimental data.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128316038","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"On classifier performance for remote sensing images compressed by different coders","authors":"G. Proskura, O. Rubel, S. Kryvenko, V. Lukin","doi":"10.32620/aktt.2023.1.07","DOIUrl":"https://doi.org/10.32620/aktt.2023.1.07","url":null,"abstract":"Remote sensing data are widely used in numerous applications. A conventional task solved using remote sensing images is their classification. The classification maps are commonly produced by some pre-trained classifiers applied either to uncompressed or compressed images where lossy compression is often needed and employed in practice due to the necessity to reduce data volume at stages of image transfer and storage. Then, the classification accuracy depends on the characteristics of an image, a classifier, and a coder used. The main subject of this paper is the factors that determine classification accuracy. One of them is compressed image quality. We fix the quality of compressed image quality characterized by the peak signal-to-noise ratio for several coders and rely on the same training approach. Our goal is twofold. First, we would like to consider classification accuracy for two approaches to classifier training: based on undistorted data and images with simulated distortions. Second, our desire is to compare the performance of different techniques of image compression. The task of this paper is to obtain an idea is it worth training the neural network classifier for uncompressed images or images of similar quality to the quality of compressed data to be classified. The coder’s influence on classification results is of special interest as well. The main results are the following. First, the classification accuracy is almost the same for classifiers trained for uncompressed and simulated compressed data for the general distortion model. Second, there is a certain difference in the classification results for different compression techniques studied. Lightly better classification results are observed for data produced by more sophisticated (modern) coders. Experiments have been carried out for two real-life three-channel Sentinel-2 images of Kharkiv and the Kharkiv region having different complexity. Four typical classes have been considered. As a conclusion, it is possible to state that either the general model of distortions must be modified or the classifier training should be performed for data produced by the corresponding compression technique.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134404682","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Numerical study of the aerodynamic characteristics of airfoil with high-lift devices","authors":"Y. Krashanitsa, Dmytro Zhyriakov","doi":"10.32620/aktt.2023.1.06","DOIUrl":"https://doi.org/10.32620/aktt.2023.1.06","url":null,"abstract":"The subject matter of this article is the aerodynamic profile of the wing with high-lift devices in the aircraft transport category. When high-lift devices are released, the aerodynamic flow of the wing changes significantly, this changes the stress-strain state of the wing. This relates not only to an increase in lift force due to a change in the curvature of the wing and an increase of the wing area, but also due to a change of the position of the center of pressure relative to the chord of the wing. The goal is to study the influence of wing high-lift devices on the aerodynamic characteristics of the profile during take-off, cruise, and landing cases using numerical methods. The obtained data will be used to determine the loads on the wing in various flight cases. The task is to determine the aerodynamic coefficients of lift and drag forces, changing the position of the pressure center during flight cases: take-off, cruise, and landing. The aerodynamic profile b737c-il was used in the analysis. The single-slot slat and double-slots flap were used in the analysis model. The numerical methods with the CAE system ANSYS Fluent were used. The solver models k-epsilon and transition SST were used for comparison. The use of numerical methods in the process of designing aircraft structures is widely used to accurately determine the aerodynamic parameters of the wing in various flight cases. The following results were obtained: the dependence of the lift coefficient on the angle of attack, the lift coefficient on the drag coefficient, and the position of the center of pressure along the chord of the profile for cruise, take-off, and landing flight cases. Conclusion. The scientific novelty of the results obtained is as follows: the use of numerical methods for determining the aerodynamic characteristics of a wing with high-lift devices in particular, determining the dependence of the position of the center of pressure relative to the chord and at different angles of attack. The obtained results will be used to determine the load on the wing, in particular the distributed load on the slats and flaps, to clarify the torque moment in the wing section where high-lift devices are used.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"144 2","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132704182","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Модель формування пористості брикетів губчастого титану на стадії спікання","authors":"L. Klymenko, V. Andreev, Olexandr Sluchak, Oleg Pryshchepov, Oleg Shchesiuk","doi":"10.32620/aktt.2023.1.03","DOIUrl":"https://doi.org/10.32620/aktt.2023.1.03","url":null,"abstract":"This article examines the peculiarities of the formation of interparticle connections in porous products based on titanium powders using sponge titanium as an example, which are used in the aviation industry and airfield management. The developed model is based on the results of a previous study, where the structure of cuboctahedral and inverse cuboctahedral clusters of packing spherical powder particles was determined at the most dense packing. During the study, a model of the fusion of particles at the points of pressing deformation due to recrystallization under the influence of high temperatures in a vacuum was developed. 4 main stages of powder briquette sintering were considered, and a mathematical model was developed for each of them. Thus, the stage of liquid evaporation is considered from the viewpoint of the cavitation effect of boiling on the surface of particles and boiling of plasticizers. Euler's film boiling formula was used to describe the forces acting on the particle surface; Tolubinsky's formula was used for bubble boiling; convective heat exchange was considered part of the final stage of sintering. The stage of the formation of metallic bonds is modeled on the basis of the results of practical studies in the REV 5.5 furnace, recrystallization based on differential scanning colorimetry on the NETZSCH STA 449F1 Proteus device, and determining the change in grain size according to the E19 ASTM scales using the Jeffers method. The diffusion stage is modeled on the basis of the approximation of the particle deformation model in the contact zones at the pressing stage using the Frenkel formula. Linear shrinkage is modeled based on direct measurement of sample sizes before and after sintering. The developed model has a certain versatility when applied to simulate the interaction of particles of metal powders under the conditions of the formation of porous briquettes, especially if the shape of the particles is close to round or spongy. The obtained result will make it possible to more accurately evaluate such a factor as the adhesion between the particles of the pressing and predict the tensile strength of the material. Additionally, due to the mathematical characterization of the peculiarities of the formation of corpuscular porosity under the conditions of sintering in a vacuum, we can design materials with differentiated porosity, as well as lay the foundations for powder 3D printing of such materials, by assembling grain by grain, or layer by layer with the adjustment of the force of particle compression one into the other.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"12 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126820802","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Вплив конструктивних параметрів термоплати на гістерезис за тепловим навантаженням","authors":"Yevhen Rohovyi, Rustem Turna","doi":"10.32620/aktt.2023.1.02","DOIUrl":"https://doi.org/10.32620/aktt.2023.1.02","url":null,"abstract":"The contact heat exchangers designed to remove heat from the cooled devices are used in mechanically pumped two-phase loops of thermal management systems for ground and space applications, a thermoplate (heat sink). After the device is turned on, it may overheat abnormally during the process of reaching a stationary operating mode. Overheating is associated with the phenomenon of thermal load hysteresis during the onset of boiling, the transition from single-phase convection to developed boiling in the evaporator of a heat sink material. This work studied the influence of the construction parameters of thermoplate on the hysteresis phenomenon at the integral level. For this purpose, a thermoplate testing methodology was implemented, which includes experiments with slow (quasi-stationary) and quick heating after turning on the device immediately at full power. Overheating of the device is possible during both \"slow\" and \"quick\" heating. The maximum overheating in the experiments performed was ~18 K. Such overheating can pose a danger to the reliability of the device. The study was performed with ammonia as a coolant on 5 models of thermoplate that differ in evaporator channel roughness, length, material, longitudinal thermal conductivity, the heat capacity of the structure, etc. The danger of overheating the device is also determined by the maximum thermal load at which the device is operated. The following conclusions were made: the greatest influence on the hysteresis parameters is the value of the evaporator channel surface roughness. Increasing the roughness reduces the risk of overheating the device, and changes the nature of the \"boiling curves\" in the thermoplate; an increase in the length and longitudinal thermal conductivity has a favorable effect on reducing the risk of overheating; the evaporator surface is made of aluminum alloy instead of stainless steel, which makes hysteresis impossible; in the case of rapid heating of the thermoplate, the maximum heat flux at steady-state has an ambiguous effect: with its increase, overheating due to hysteresis first increases, and in the case of further increase, it decreases and may disappear altogether. A significant increase in the maximum heat flux compared to the heat flux at the beginning of boiling reduces the danger of hysteresis affecting the overheating of the device. The results of this work provide recommendations on how to avoid the dangerous overheating of the device due to the hysteresis phenomenon.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126660596","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Аналіз точності експериментального визначення ККД вентилятора з використанням вимірювачів крутильного моменту","authors":"Kostiantyn Podgors’ky, Sergiy Yepifanov","doi":"10.32620/aktt.2023.1.04","DOIUrl":"https://doi.org/10.32620/aktt.2023.1.04","url":null,"abstract":"The subject of research in this article is the processes of experimental determination of the characteristics of fans of turbojet bypass engines with a high and ultra-high bypass ratio. The goal is to substantiate the need to use a method based on the determination of torque, and the formation of requirements for the accuracy of its measurement. Tasks: determination of the relationship between measurement errors and the accuracy of determining the efficiency and air flow, analysis of the accuracy of alternative methods for organizing measurements and calculating the indicated parameters, comparative study of these methods, and the formation of recommendations for their practical use. For this, analytical methods of error analysis based on the methods of analysis of random variables are used. The following results were obtained: formulas that relate the errors in the calculation of efficiency and consumption with errors in the measured parameters (mathematical models of errors), and determine requirements to the torque measurement precision, which must determine the efficiency with a specified precision. The scientific and practical novelty of the results obtained is as follows: mathematical models of errors in determining the efficiency and flow in the fan have been formed, which relate the errors in the results of calculations with the errors in the measured parameters; because of the use of these models, experimental methods for determining the characteristics of compressors and fans have been developed; for the first time, an analytical expression was obtained that determines the requirements for the measurement error of torque to experimentally determine the efficiency of fans. It is shown that to determine the efficiency with an accuracy of 0.5 %, the accuracy of torque measurement even in the absence of other measurement errors cannot be worse than 0.5 %, and taking into account the perspective of measuring temperatures and pressures with relative standard deviations σδp = 0.02 % and σδT = 0.25 %, the standard deviation of the torque measurement error should not be more than 0.24 %.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"44-46 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132175148","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Ідентифікатор передпомпажних станів компресора авіаційного ГТД","authors":"Serhii Yenchev, Serhii Taku","doi":"10.32620/aktt.2022.5.05","DOIUrl":"https://doi.org/10.32620/aktt.2022.5.05","url":null,"abstract":"Surging is a dangerous operating mode of the compressor; in this mode, destabilization and flow stall occur, causing intense pressure fluctuations of the working fluid in the flow path or gas-dynamic shocks. Surging phenomena in gas turbine engines lead to a loss of thrust, are accompanied by an increase in the temperature of gases in front of the turbine and an increase in the level of vibration because of large amplitudes of pressure pulsations and mass flow rates along the engine path. The possibility of occurrence of these phenomena is a serious obstacle to increasing the reliability of gas turbine engines, including flight safety in general. The study of non-stationary processes in compressors shows that surge is preceded by such phenomena as pre-surge and rotating stall, which are called the pre-surge state of an aircraft GTE compressor. The study aims to develop informative criteria for the timely detection of the pre-surge state of the compressor of an aircraft gas turbine engine and to build an anti-surge algorithm for the functioning of the proposed identifier based on the developed criteria. To assess the stability of pressure pulsation periodicities, it is proposed to process and compare the signals received from fast-response sensors located in the compressor. In this article, informative criteria are formed for identifying the pre-surge state of an aircraft GTE compressor. The first criterion is the level of stability of the periodic component of pressure fluctuations. The second criterion is the limit of the relative range of pressure pulsations in the compressor. With the help of the obtained criteria, the pre-surge area is divided into pre-surge, weak stall, and intense stall. Such detailing makes it possible to prevent erroneous wear (in high-cost modes) and premature wear (in case of non-intensive disruption) of the anti-surge control system. Based on the criteria obtained, an algorithm for anti-surge adjustment was developed, according to which the anti-surge system is prepared for testing when a pre-surge or weak stall occurs in the compressor flow path, and is triggered when an intense stall occurs. Based on the anti-surge algorithm, a scheme for identifying the pre-surge states of an aircraft GTE compressor is proposed in the form of a three-level alarm and protection system. Recommendations for the practical implementation of the identifier are described.","PeriodicalId":418062,"journal":{"name":"Aerospace technic and technology","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130697935","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}